[1]刘庆,陈林泉,王建儒,等.含锆或氢化锆推进剂的能量特性分析[J].固体火箭技术,2019,42(01):54-59.
 LIU Qing,CHEN Linquan,WANG Jianru,et al.Analysis of energy characteristics of the propellants containing zirconium or its hydride[J].Journal of Solid Rocket Technology,2019,42(01):54-59.
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含锆或氢化锆推进剂的能量特性分析

参考文献/References:

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[2]陈林泉,毛根旺,陈军涛.采用高低燃温组合装药降低喷管内表面温度和烧蚀研究[J].固体火箭技术,2008,31(6):599-601.CHEN Linquan,MAO Genwang,CHEN Juntao.Research on reducing inner surface temperature and ablation rate of nozzle by means of high and low temperature combined propellant[J].Journal of Solid Rocket Technology,2008,31(6):599-601.
[3]赵生国,宋明纲.高固体NEPE高能推进剂研究[C]//中国宇航学会固体火箭推进24届年会文集.2007.ZHAO Shengguo,SONG Minggang.Research on high solid NEPE high energy propellant[C]//The 24th Annual Meeting of Solid Rocket Propulsion of China Academy of Aerospace Society,2007.[4]Lempert D B,Nechiporenko G N,Manelis G B.Energetic capabilities of highdensity composite solid propellants containing zirconium or its hydride[J].Combustion Explosion & Shock Waves,2011,47(1):45-54.
[5]Lempert D B,Brambilla M,Deluca L T.Ballistic effectiveness of Zrcontaining composite solid propellants as a function of binder nature and mass fraction[J].Progress in Propulsion Physics,2013(4):15-32.
[6]Alekseev A P,Lempert D B,Nemtsev G G,et al.Combustion of zirconiumcontaining model compositions of solid propellant[J].Russian Journal of Physical Chemistry B,2012,5(6):997-999.?
[7]Min B S,Hyun H S.Study on combustion characteristics and performance of HTPB/AP propellants containing zirconium[J].Journal of Propulsion &Power,2015,28(1):211-213.
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[9]李猛,赵凤起,徐司雨,等.含金属氢化物的复合推进剂能量特性[J].固体火箭技术,2014,37(1):86-90.LI Meng,ZHAO Fengqi,XU Siyu,et al.Energetic characteristics of composite propellant containing different metal hydride[J].Journal of Solid Rocket Technology,2014,37(1):86-90.
[10]YANG Yanjing,ZHAO Fengqi,YUAN Zhifeng,et al.On the combustion mechanisms of ZrH2 in double-base propellant[J].Physical Chemistry Chemical Physics,2017,48(19):32597-32604.

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更新日期/Last Update: 2019-03-21
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